TW323319B - - Google Patents

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Publication number
TW323319B
TW323319B TW084110282A TW84110282A TW323319B TW 323319 B TW323319 B TW 323319B TW 084110282 A TW084110282 A TW 084110282A TW 84110282 A TW84110282 A TW 84110282A TW 323319 B TW323319 B TW 323319B
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TW
Taiwan
Prior art keywords
flow path
flow
blade
turbine
fluid
Prior art date
Application number
TW084110282A
Other languages
Chinese (zh)
Original Assignee
Westinghouse Electric Corp
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Publication of TW323319B publication Critical patent/TW323319B/zh

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

3 扣 319 - A7 ________B7 五、發明説明7 ο "~~一— 發明背景 本發明係關於-種氣渦輪固定葉片，明確而言本發明係 關於一種具有曲狀冷卻空氣流路之氣渦輪機固定葉片，此 葉片具有高冷卻效果。 —氣渦輪使用喊排圚週排列在渦輪機段的複數個固定葉 片，因爲這種葉片承受燃燒段排放的高熱燃氣、因此冷卻 迈些葉片極爲重要。通常使冷卻空氣流過葉面内的槽即可 達到冷卻目的。 根據一種方法，使用一個或多個管狀插入物插入各葉面 槽，以使插入物與葉面壁之間形成圍繞插入物之流路。插 入物具有數個分佈在其四週之孔’藉此在這些流路中分送 冷卻空氣。 根據另一方法，各葉面包括數條徑向延伸流路，通常是3 條以組成一排曲狀流路。供給葉片外覆環之冷卻空氣進入 第一流路並徑向向内流動，直到其到達葉片内覆環β冷卻 空氣的第一部分經由内覆環離開葉片而到達一槽，此横位 於各相鄰轉子圊盤排之間《槽中的冷卻空氣可冷卻圓盤表 面’。冷卻空氣之第二部分則反向並徑向向外流過第二流 路，直到其到達外覆環，在那裡再改變方向，並徑向向内 流過余三流路，最後自第三流路通過葉面後緣的孔離開葉 片d .. 已試過多種方法來增加冷卻空氣流過曲狀流路k效季， 其中一種方法是使用從形成流路的壁延伸出的散'熱'片。已 > 試過將延伸出的散熱片使其與流向垂直或成一角度，但是 本紙張尺度逋用中國國家梂準（CNS )八4規《格（210X2.97公釐） (請先聞讀背面之注f項再填寫本頁：> 訂 經濟部中央揉準局負工消費合作社印装 A7 B7 經濟部中央標準局工消費合作杜印製 五、發明説明（〇 這種設計在氣渦輪機中卻不足以冷卻葉面，因爲葉面的截 面積較大，而這會降低速度，以及冷卻空氣流過流路時的 熱傳係數。這種設計之冷卻力，當它配合高壓力比壓縮機 使用時還有一缺點，因爲從這種蜃縮機送出的冷卻空氣溫 度較高。 ‘ 此外，冷卻空氣吸收葉面的熱會使其變熱。因此當冷卻 空氣到達最後的曲狀流路時，它可能已變得太熱而無法冷 卻葉面後緣，特別是若使用3條以上這種流路時，而且葉面 冷卻所導致的冷卻空氣過熱，會使得冷卻空氣太熱而無法 冷卻圓盤間的槽。 —種可能解決這些問題的方法是大幅增加供給葉面的冷 卻空氣，藉以增加冷卻空氣流過通道之流率。但我們並不 希望冷卻空氣的這種大幅增加，雖然這種冷卻空氣流最後 進入流過渦輪部分的高熱氣流，但是從冷卻空氣中得到的 有效功卻很小，因爲冷卻空氣不易在燃燒器部分加熱。因 此爲了達到高效率，使冷卻空氣的用量減至極小係極爲重 要的事。 因此期望提供一種冷卻設計，可大幅提昇冷卻空氣流過 氣渦輪旋轉葉片的葉面之冷卻效率。也期望能防止冷卻空 氣，部分之過熱，此部分用於冷卻葉面後緣部分；與防止冷 卻空氣部分之過熱，此部分用於冷卻轉子圓盤。 發明之概述 -η 因此本發明之一般目標是期望提供一種冷卻設計’，可大 -5- 本紙張尺度適用中國國家梯準（CNS ) Α4规格（2ι〇χ297公釐） (請先Μ讀背面之注意事項再填寫本頁) *11 M濟部中央樣準局貝工消费合作杜印製 ~ A7 ._;__B7 五、發明説明（~~3) ~~ --- 幅提昇冷卻空氣流過氣竭輪旋轉葉片的葉面之冷卻效率， 並防止冷卻空氣部分之過熱，此部分用於冷卻葉面後緣部 分及轉子圓盤。 簡言之’本發明的此目標以及其他目標之完成，是在源 輪機中包括：一壓縮機’以產生壓縮空氣；一燃燒器，以 加熱壓縮空氣之第一部分，藉此產生熱壓縮燃氣；及-渴 輪’以膨脹熱壓縮燃氣。葉片中具有至少第_及第二冷卻 空氣流尊，第一流路具有裝置，以容納壓縮空氣之第二部 分。第-及第二流路循序作流趙流通，藉此壓縮空氣之第 二部分循序流過第-流路，接著流過第二流路。第二流路 2有裝£，以容納旁通第一流路之壓'縮空氣之第三部分， 藉此混合壓縮空氣之第二及第三部分，並流過第二流路。 根據本發明（特色’葉片又包括：内覆環、外覆環及一 導管，延伸通過内復環、外覆環及一條冷卻空氣流路。此 外在葉片内覆環及一轉子間形成一槽。導管具有一出口， 此出口與槽作流體流通，藉此導管引導壓縮空氣之第四部 分流過内復環'外復環及一條通至槽之流路。 稂據本發明之另一特色，葉片又包括：⑴一第三冷卻空 氣流路，第一流路係循序與第三流路作流過流通，藉此壓 缩♦空氣t第二部分循序自第三流路流到第一流路，圍繞 第二及第三流路之第一及第二壁，複數個第一组散熱 片，自一面壁延伸進入第三流路，及（iv)複數個第二组鼻熱 片’自一面壁延伸進入第二流路。第二及第三流路-皆徑向 延伸通過葉片，而第—及第二組散熱片與徑向成一角度。 本紙張;財CNS )^^-( 21_7 公爱） (請先閱讀背面之注$項再填寫本頁) 訂 經濟部中央梯準局貝工消費合作社印製 Α7 Β7 五、發明説明（4) 附圈之簡單説明 囷1是部分氣源輪縱向剖面之部分示意圖，該滿輪具有根 據本發明<第三排渦輪葉片。 囷2是圖1之中嚆近第三排葉片之詳圖，爲了簡潔因此省 略冷卻空氣散熱片。 （ 囷3是囷2之中第三排葉片之剖面圖，其顯示冷卻空氣散 熱片之排列，爲了簡潔因此省略圊盤槽冷卻空氣供給管。 圖4是擷取囷2IV-IV線段之圖型。 圖5疋擷取圖3 V-V線段之橫向剖面圖。 圖6是擷取圖3VI-VI線段之剖面囷。， 圖7是囷3前3條冷卻空氣流路之詳圖。 較佳具體實例説明 參考以下附圖，圖1是部分氣渦輪之縱向剖面囷。氣渦輪 之主要元件是：一壓縮段1’ 一燃燒段2及一渦輪段圖中 轉子4係位於中弗躞穿過這3段，歷縮機段1由殼7及8组成， 該殼圍繞固定葉片12及旋轉葉片π，這二種葉片係交替排 列。固定葉片12固定在殼8而旋轉葉片13固定在連接轉子4 的fiT盤上。 燃燒段2包括：一略呈殼形的__外殼9，此外殼形成一燃燒 室14，殼8後端及一内殼25共同圍繞轉子4的一部分。草數 個包含在燃燒室内的燃燒器15及導管16，導管16連-接燃燒 1 器15及渦輪機段3。燃料35可以是液態或氣態，如提煉油或 本紙張尺度適用中國國家標準（CNS )八4規《格（210X297公釐） (婧先閲讀背面之注意事項再填寫本頁)3 Buckle 319-A7 ________B7 5. Description of the invention 7 ο " ~~ 一 —Background of the invention The present invention relates to a fixed blade for a gas turbine, specifically the invention relates to a fixed gas turbine with a curved cooling air flow path Blade, this blade has a high cooling effect. -The gas turbine uses a plurality of fixed blades arranged in the turbine section around the exhaust row. Because this blade withstands the hot gas emitted by the combustion section, it is extremely important to cool the blades. Normally, cooling air can be flowed through the grooves in the blade surface to achieve cooling purpose. According to one method, one or more tubular inserts are inserted into each foliar groove so that a flow path around the insert is formed between the insert and the foliar wall. The insert has several holes distributed around it to thereby distribute the cooling air in these flow paths. According to another method, each leaf surface includes several radially extending flow paths, usually 3 to form a row of curved flow paths. The cooling air supplied to the outer cover ring of the blade enters the first flow path and flows radially inward until it reaches the inner cover ring of the blade. The first part of the cooling air leaves the blade through the inner cover ring and reaches a slot, which is located horizontally on each adjacent rotor Between the disk rows, the cooling air in the groove can cool the surface of the disk. The second part of the cooling air is reversed and flows radially outward through the second flow path until it reaches the outer ring, where it changes direction, and flows radially inward through the remaining three flow paths, and finally from the third flow path Leave the blade d through the hole in the trailing edge of the leaf surface .. Various methods have been tried to increase the cooling air flow through the curved flow path. One of the methods is to use a diffused 'heat' sheet extending from the wall forming the flow path. . I have tried to extend the extended heat sink so that it is perpendicular or at an angle to the flow direction, but the size of this paper uses the Chinese National Standard (CNS) 8 4 rule "grid (210X2.97mm) (please read first Note f on the back and then fill in this page: > Ordered by the Ministry of Economic Affairs, Central Bureau of Standardization and Accreditation of the Consumer Labor Cooperative A7 B7 Printed by the Ministry of Economic Affairs, Central Bureau of Standards, Industrial and Consumer Cooperation V. Invention description (〇 This design is used in gas turbines) It is not enough to cool the blade surface because the cross-sectional area of the blade surface is large, which will reduce the speed and the heat transfer coefficient of the cooling air flowing through the flow path. The cooling power of this design, when it is matched with a high pressure ratio compressor There is also a disadvantage when using it, because the temperature of the cooling air sent from this kind of shrinking machine is higher. In addition, the cooling air absorbs the heat of the leaf surface and makes it hot. Therefore, when the cooling air reaches the final curved flow path, It may have become too hot to cool the trailing edge of the blade, especially if more than three such flow paths are used, and the cooling air caused by the cooling of the blade is too hot, making the cooling air too hot to cool the disc Slot -One possible solution to these problems is to increase the cooling air supply to the blade surface significantly, thereby increasing the flow rate of cooling air through the channel. But we do not want this large increase in cooling air, although this cooling air flow finally enters The high heat flow through the turbine part, but the effective work obtained from the cooling air is very small, because the cooling air is not easy to heat the burner part. Therefore, in order to achieve high efficiency, it is extremely important to reduce the amount of cooling air to a minimum Therefore, it is desirable to provide a cooling design that can greatly improve the cooling efficiency of the cooling air flowing through the blade surface of the rotating blades of the air turbine. It is also desirable to prevent the cooling air from being partially overheated, which is used to cool the trailing edge portion of the blade surface; and to prevent Overheating of the cooling air part, this part is used to cool the rotor disc. SUMMARY OF THE INVENTION-η Therefore, the general goal of the present invention is to provide a cooling design, which can be applied to the Chinese National Standard (CNS). Α4 specification (2ι〇χ297mm) (Please read the notes on the back before filling this page) * 11 M Printed by the Central Bureau of Standards, Beigong Consumer Cooperation ~ A7 ._; __ B7 V. Description of the invention (~~ 3) ~~ --- Improves the cooling efficiency of the cooling air flowing through the blade surface of the rotating blade of the exhaust wheel, and To prevent overheating of the cooling air part, this part is used to cool the trailing edge part of the blade surface and the rotor disc. In short, the accomplishment of this goal of the present invention and other goals is to include: a compressor in the source turbine to produce Compressed air; a burner to heat the first part of the compressed air, thereby generating hot compressed gas; and-Thirsty wheel 'to expand the hot compressed gas. The blade has at least the first and second cooling air flow respect, the first The first-class path has a device to accommodate the second part of the compressed air. The first and second flow paths sequentially flow through the flow, whereby the second part of the compressed air flows sequentially through the first flow path and then flows through the second flow path . The second flow path 2 is equipped to accommodate the third portion of the compressed air bypassing the first flow path, thereby mixing the second and third portions of the compressed air and flowing through the second flow path. According to the present invention (featured), the blade further includes: an inner covering ring, an outer covering ring and a duct, extending through the inner complex ring, the outer covering ring and a cooling air flow path. In addition, a groove is formed between the inner covering ring and a rotor of the blade The duct has an outlet, which is in fluid communication with the groove, whereby the duct guides the fourth part of the compressed air to flow through the inner compound ring 'outer compound ring and a flow path to the slot. 稂 According to another feature of the invention , The blades also include: (1) a third cooling air flow path, the first flow path flows through the third flow path in sequence, thereby compressing the second part of the air t flows from the third flow path to the first flow path, Around the first and second walls of the second and third flow paths, a plurality of first sets of fins extend from one wall into the third flow path, and (iv) a plurality of second sets of nasal heat sheets' from one wall Extends into the second flow path. The second and third flow paths-both extend radially through the blades, and the first-and second set of fins are at an angle to the radial direction. This paper; Cai CNS) ^^-(21_7 Gongai ) (Please read the note $ item on the back before filling in this page) Printed by the Industrial and Consumer Cooperative Society Α7 Β7 V. Description of the invention (4) Brief description of the attached ring 囷 1 is a partial schematic view of the longitudinal section of part of the air source wheel, the full wheel has a third row of turbine blades according to the present invention. Fig. 2 is a detailed view of the third row of blades in Fig. 1. For simplicity, the cooling air fins are omitted. (囷 3 is a cross-sectional view of the third row of blades in 囷 2, which shows the arrangement of cooling air fins. For simplicity, therefore, the cooling air supply pipe of the tray groove is omitted. Figure 5 is a cross-sectional view of the VV line segment in Figure 3. Figure 6 is a cross-sectional view of the line segment VI-VI in Figure 3. Figure 7 is a detailed view of the first three cooling air flow paths in Figure 3. Preferred specific examples Description refers to the following drawings, Figure 1 is a longitudinal section of a part of the gas turbine. The main components of the gas turbine are: a compression section 1 ', a combustion section 2 and a turbine section. In the figure, the rotor 4 is located in the middle of the three The section 1 of the shrinking machine is composed of shells 7 and 8. The shell surrounds the fixed blade 12 and the rotating blade π, which are alternately arranged. The fixed blade 12 is fixed to the shell 8 and the rotating blade 13 is fixed to the rotor 4 On the fiT disk. The combustion section 2 includes: a slightly shell-shaped outer shell 9, which forms a combustion chamber 14, the rear end of the shell 8 and an inner shell 25 surround a part of the rotor 4. Several grasses are included in the combustion The burner 15 and the duct 16 in the room are connected to the burner 15 and the turbine section 3. 35 can be liquid or gaseous, such as refined oil or scale of this paper applies China National Standard (CNS) eight 4 rules "format (210X297 mm) (Jing first read the note and then fill in the back of this page)

-IT 經濟部中央揉準局—工消費合作社印装 '- A7 _____B7___ 五、發明説明（5) 天然瓦斯’經由一燃料喷嘴34進入各燃燒器15並在其中燃 燒產生熱壓縮燃氣3〇。 渴輪3由圍繞内殼u之外殼1〇組成，内殼^圍繞數排固定 葉片及數排旋轉葉片，這些葉片圓遇狀排列以圍繞轉子4的 中心線。固定葉*片固定在内殼U而旋轉葉片固定在圓盤， 圓盤則组成部分轉子4之渦輪段。 、 運轉時壓縮機段1引入周圍空氣並壓縮它。進入壓縮機的 部分空氣，於作了部分壓縮後即分送出去，用以冷卻渦輪 段3内的2-4排固定葉片，以下要藉著參考第三排葉片22而 詳細説明。剩下的壓縮空氣20則自壓縮段1排出並進入燃燒 室14。自燃燒室14抽出部分壓·縮空氣2〇用以冷卻第一排固 定葉片’轉子4及連接轉子的旋轉葉片。燃燒室中剩下的 壓縮空氣20則分配至各燃燒器15。 在燃燒器15中燃料35與壓縮空氣混合並燃燒產生熱壓縮 氣30。熱壓縮氣30流入導管16接著流過渦輪段3的各排固定 葉片及旋轉葉片’燃氣在其中膨脹並產生動力以驅動轉子 4,膨服燃氣31接著從渦輪3中排出。 本發明在探討固定葉片之冷卻，並藉著參考第三排固定 葉片22而加以詳細説明。如圖1所示，經由一條管子24從級 間分'換歧管18抽取部分19流過壓缩機1的空氣，並導入满輪 段3»在渦輪段3中，冷卻空氣L9進入位於内殼u及外毅1〇 之間的歧管26，冷卻空氣19通過歧管26進入第三排葉片 22。 - ! 如圖2 -5所示，葉片22由一葉面部分37組成，其各位於 本紙張又度逍用中國國家揉準（CNS ) Α4規格（210X297公釐） (锖先閱讀背面之注意^項再填寫本I ) 訂 .^! 經濟部中央揉準局貝工消費合作社印製 A7 B7 五、發明説明（6) 内外覆環36，38之間。此葉面部份具有連接内復環36之第 一端及連接外覆環38之第二端。支律軌56，57用以連接葉 片22與渦輪内殼11。如囷5所示，葉片22的葉面部分37之形 成，係由：一大致呈凹狀的壁46,其形成葉面的壓力表 面，及一大致呈*凸狀的壁47,其形成葉面的吸力表面。在 其上游端及下游端，壁46，47分別形成葉面37的前緣40及 後緣41。 葉面37大致上是中空的，如圖3，5所示徑向延伸壁65-6 8 在壁46 ’ 47之間延伸’並將葉面37的内部，分成5個徑向延 伸的冷卻空氣流路51-55。外覆環38的第一開口 58允許冷卻 空氣19的一部分80進入第一流路51，第一流路51與前緣相 鄰排列著。重要的是壁65-68並非一直從内覆環3 6延伸至外 覆環3 8，相反地，它沒到達内或外覆環（依特別壁而定） 就停止以形成一連接流路，以允許各流路5卜55與相鄰流路 流通。因此曲狀排列流路51-55，以使冷卻空氣8〇循序從流 路5 1流到流路52 ’ 53，54最後到達與後緣41相鄰的流路 55 »分別在各流路5 1-55及内外覆環之間，使冷卻空氣於進 入相鄰流路前作約180°的轉向。 冷卻空氣從流路55分成複數個小流路87，並通過複數個 軸•向伸流路49離開葉片22，該軸向延伸流路係在葉面37 的後緣41中，如圖3所示。離開—葉片22時，冷卻空氣87的小 流路與流過渦輪機段3的熱燃氣30混合。 . 根據本發明之重要特色’外-覆環38中有第二開口·4.8，第 一開口 48允許冷卻空氣19的第二部分83自歧管26分別旁通 本紙張尺度適用中國國家搮準（CNS ) A4規格（210X297公漦） I!-----r------iT------1- (請先閱讀背面之注意事項再填寫本頁) 經濟部中央梂準局貝工消費合作社印掣 A7 ___— —_B7______ 五、發明説明（7) 第一51及第二流路52，而直接進入第三流路53在第三流路 中’混合冷卻空氣的第80及83部分以增加冷卻空氣分別流 過第三53、第四54及第五55流路的量。更重要的是，旁通 的冷卻空氣83冷卻該冷卻空氣80，該冷卻空氣80已吸收大 量的熱，因爲其•分別流過第一 51及第二流路52。因此雖然 在本發明之較佳具體實例中，共有5條曲狀流路5 i—55，仍 可防止冷卻空氣到達第五流路55時產生過熱，以確保流路 55中冷卻空氣的溫度夠低，足以冷卻葉面37的後緣部分 41。 如圖2所示’一條中空徑向延伸的圓槽冷卻空氣供給管 45，分別延伸通過内覆環36、外覆環3,8及第二流路52。管 子45—端的入口 76可容納來自歧管26的冷卻空氣19的第三 部分’而管子45另一端的出口 77則排放冷卻空氣84至一槽 70 ’此槽位於内覆環36及轉子4的圓盤42，43之間。第二排 旋轉葉片21連接圓盤42，而第三排旋轉葉片23連接圊签 43。 用螺釘（未顯示）使級間密封殼71與内覆環36連接，此 殼並支# 一密封72。複數個曲折散熱片73在環狀流路内延 伸，此流路位於密封72及臂74，75之間，臂74，75則分別 自册i42，43延伸。密封粒71控制冷卻空氣84流出槽7〇的 量6明確而言，殼71中的流路50引導冷卻空氣離開槽7〇， 並從這裡分成2條流路85，86 \第一流路85徑向向外流入流 過渴輪段3的熱燃氣30。如此冷卻空氣85即可冷卻圓'盤42的 後表面，並防止熱燃氣30流過圓盤表面。 ' -10- 本紙張尺度逍用中國國家梂準（CNS ) A4规格（210X297公董 1 (請先閲讀背面之注意事項再填寫本頁) 訂 32S319 A7 B7 經濟部中央揉準局貝工消費合作社印製 五、發明説明8) 第二流路86流過環狀曲折密封流路，接著徑向向外流入 流過渦輪段3的熱燃氣30。如此冷卻空氣86即可冷卻圓盤43 的前表面’並防止熱燃氣30流過圓盤表面。 因爲流過第三排旋轉葉片23的熱燃氣30壓力比流過第二 排旋轉葉片21於熱燃氣30壓力低，大致上若非密封72則所 有的冷卻空氣會向下流到圓盤43，而密封72可防止其發 生，藉此確保上游圓盤42的冷卻。 圓盤槽冷卻空氣供給管45允許冷卻空氣84流過葉片22時 吸走最小的熱，因此根據本發明之重要特.色，管子45允許 冷卻空氣84自歧管26導入級間槽70時，大致上不升高冷卻 空風溫度’藉此確保其冷卻圓盤42，. 43之能力。如上所 述’在滴輪中这特別重要’因爲供給歧管26的冷卻空氣19 溫度已相當高了。 根據本發明’複數個散熱片60-64有時稱爲擾流片，從壁 46，47突出在流路51_55，如圖3，5，6，7所示。在圖2 中，散熱片60-64最好大致上沿著整個流路51-55高度分佈》 此外如囷3所示，散熱片60-64最好大致上沿著流路5 1-55的 整個軸向長度延伸。圖6顯示第二流路52的散熱片61，但它 卻是各流路中散熱片的典型排列方式。在圖6中散熱片61從 葉，面37對面的壁46，47橫向突出·第二流路，最好具有約 10%流路寬度的高度。散熱片61是隔開的，以使自壁46突 出的散熱片排列在自壁47突出的散熱片之間》散^片6J3-64 增加冷卻空氣80，83流過流路時的擾動，以增加其-冷卻效 率〇 -11- 本紙張尺度適用中國國家揉準（CNS ) A4规格（2丨0X297公釐） (請先閏讀背面之注意事項再填寫本頁} t 訂 蹲： A7 Β7 五、發明説明（9) 根據本發明之一重要特色，散熱片60-64與冷卻空氣流過 流路51-55之流向成一角度，冷卻空氣基本上是徑向，因此 如圖7所示，散熱片與徑向間的角度是銳角a。在較佳具體 實例中與向外徑向形成的銳角A約在45-60。之間，大多是 45° 。此情況發生於，散熱片自上游延伸至熱壓縮氣30之 流向，於徑向向外成一角度’如第一、第三及第四流路； 或散熱片向上延伸於徑向向外成一角度，如第二及第四流 路0 在第一流路51中冷卻空氣80從外覆環38徑向向内流到内 覆環36。根據本發明之另一重要特色，第一流路51的散熱 片60是有角度的，以使其徑向向内v即朝向内覆環％延 伸’此發生於散熱片在上游方向朝著前緣延伸時，如圈3， 7所示。因此當冷卻空氣80徑向向内流動時，即引導其流向 前緣，如囷7的箭號81所示。因此散熱片60不僅增加冷卻空 氣80的擾動，而且可引導其貼著前緣4〇,以增加前緣之冷 卻效率。這很重要因爲流過渦輪段3的熱燃氣30會直接衝擊 前緣40,而前緣是葉面37中最容易產生過熱的一部分。 經濟部中央標準局負工消費合作杜印製 (請先閲讀背面之注意事項再填寫本頁) 在第五流路55中冷卻空氣80，83從内覆環3 6徑向向内流 到外覆環3 8。因此使用一種類似第一流路5 1中的排列，使 第，五1 4路5 5的散熱片6 4成一角度，以使其徑向向外，即朝 向外覆環38延伸’此發生於散熱片在下游方向朝後緣41延 伸時，如圖3所示。因此當冷卻空氣8〇，83徑向向外尊動 時’即引導其貼著後緣40，以增加後緣之冷卻效率· β這也 很重要因爲其剖面較薄，而後緣41是葉面37中另一個容易 •12- - t ί ι * /-Printed by the Central Bureau of Industry and Information Technology of the Ministry of Economic Affairs-Industrial and Consumer Cooperatives '-A7 _____B7___ V. Description of the invention (5) Natural gas' enters each burner 15 through a fuel nozzle 34 and burns therein to produce hot compressed gas 30. The thirst wheel 3 is composed of an outer shell 10 which surrounds an inner shell u. The inner shell ^ surrounds several rows of fixed blades and several rows of rotating blades, which are arranged in a circle to surround the centerline of the rotor 4. The fixed blades are fixed to the inner shell U and the rotating blades are fixed to the disc, which constitutes the turbine section of the rotor 4. 1. During operation, the compressor section 1 introduces ambient air and compresses it. Part of the air that enters the compressor is distributed after being partially compressed to cool the 2-4 rows of fixed blades in the turbine section 3. This will be explained in detail below by referring to the third row of blades 22. The remaining compressed air 20 is discharged from the compression section 1 and enters the combustion chamber 14. Part of the compressed and contracted air 20 is drawn from the combustion chamber 14 to cool the first row of stationary blades' rotor 4 and the rotating blades connected to the rotor. The compressed air 20 remaining in the combustion chamber is distributed to each burner 15. In the burner 15, the fuel 35 is mixed with compressed air and burned to generate hot compressed gas 30. The hot compressed gas 30 flows into the duct 16 and then flows through the rows of fixed and rotating blades of the turbine section 3 where the gas expands and generates power to drive the rotor 4, and the expanded gas 31 is then discharged from the turbine 3. The present invention is discussing the cooling of the stationary blades, and will be described in detail by referring to the third row of stationary blades 22. As shown in FIG. 1, a portion of the air flowing through the compressor 1 is extracted from the interstage branching manifold 18 through a tube 24 and introduced into the full wheel section 3 »In the turbine section 3, the cooling air L9 enters the inner shell The manifold 26 between u and Waiyi 10, the cooling air 19 enters the third row of blades 22 through the manifold 26. -! As shown in Figure 2-5, the blade 22 is composed of a leaf surface part 37, which is located on this paper and is used in the Chinese National Standard (CNS) Α4 specification (210X297mm) (Read the note on the back first ^ Please fill in this item I) Order. ^! A7 B7 printed by the Beigong Consumer Cooperative of the Central Bureau of Economic Development of the Ministry of Economic Affairs V. Description of the invention (6) Between the inner and outer covering rings 36, 38. This leaf portion has a first end connected to the inner complex ring 36 and a second end connected to the outer cover ring 38. The branch rails 56, 57 are used to connect the blades 22 and the turbine inner casing 11. As shown in Fig. 5, the formation of the leaf surface portion 37 of the blade 22 is made up of: a generally concave wall 46, which forms the pressure surface of the leaf surface, and a generally convex wall 47, which forms the leaf Suction surface. At its upstream and downstream ends, the walls 46, 47 form the leading edge 40 and trailing edge 41 of the leaf surface 37, respectively. The leaf surface 37 is substantially hollow, as shown in FIGS. 3 and 5, the radially extending walls 65-6 8 extend between the walls 46'47 'and divide the inside of the leaf surface 37 into 5 radially extending cooling air Flow path 51-55. The first opening 58 of the outer cover ring 38 allows a portion 80 of the cooling air 19 to enter the first flow path 51, which is arranged adjacent to the leading edge. The important thing is that the walls 65-68 do not extend all the way from the inner cover ring 36 to the outer cover ring 38, on the contrary, it stops before reaching the inner or outer cover ring (depending on the special wall) to form a connecting flow path, In order to allow each flow channel 55 to 55 and the adjacent flow channel to circulate. Therefore, the flow paths 51-55 are arranged in a curved manner so that the cooling air 80 flows sequentially from the flow path 51 to the flow paths 52'53, 54 and finally reaches the flow path 55 adjacent to the trailing edge 41. Between 1-55 and the inner and outer cover rings, the cooling air is turned about 180 ° before entering the adjacent flow path. The cooling air is divided into a plurality of small flow paths 87 from the flow path 55, and leaves the blade 22 through a plurality of shafts to the extension flow path 49, which is located in the trailing edge 41 of the blade surface 37, as shown in FIG. 3 Show. Upon leaving the blade 22, the small flow path of the cooling air 87 is mixed with the hot gas 30 flowing through the turbine section 3. According to an important feature of the present invention, 'outer-cover ring 38 has a second opening 4.8, the first opening 48 allows the second portion 83 of the cooling air 19 to bypass the manifold 26 from the manifold 26, respectively. CNS) A4 specification (210X297 gong) I! ----- r ------ iT ------ 1- (please read the precautions on the back before filling in this page) Central Ministry of Economic Affairs Bureau Beigong Consumer Cooperative Seal A7 ___— —_B7 ______ V. Description of the invention (7) The first 51 and the second flow path 52, and directly enter the third flow path 53 in the third flow path 'mixed cooling air 80th And 83 to increase the amount of cooling air flowing through the third 53, fourth 54 and fifth 55 flow paths, respectively. More importantly, the bypass cooling air 83 cools the cooling air 80, which has absorbed a large amount of heat because it flows through the first 51 and the second flow path 52, respectively. Therefore, although there are five curved flow paths 5 i-55 in the preferred embodiment of the present invention, it can still prevent the overheating of the cooling air when it reaches the fifth flow path 55 to ensure that the temperature of the cooling air in the flow path 55 is sufficient Low enough to cool the trailing edge portion 41 of the blade surface 37. As shown in FIG. 2, a hollow radial cooling air supply pipe 45 extending radially extends through the inner cover ring 36, the outer cover rings 3, 8 and the second flow path 52, respectively. The inlet 76 at the end of the tube 45 can receive the third part of the cooling air 19 from the manifold 26 'and the outlet 77 at the other end of the tube 45 discharges the cooling air 84 to a slot 70' which is located in the inner cover ring 36 and the rotor 4 Between disks 42, 43. The second row of rotating blades 21 is connected to the disk 42, and the third row of rotating blades 23 is connected to the flashcard 43. The interstage sealing shell 71 is connected to the inner cover ring 36 with screws (not shown), and this shell supports # 1 seal 72 in parallel. A plurality of meandering fins 73 extend in the annular flow path, which is located between the seal 72 and the arms 74, 75, and the arms 74, 75 extend from the i42, 43, respectively. The sealing particles 71 control the amount of cooling air 84 flowing out of the groove 70. Specifically, the flow path 50 in the shell 71 guides the cooling air out of the groove 7 and is divided into two flow paths 85, 86 \ the first flow path 85 diameter from here Hot gas 30 flowing through the thirsty wheel section 3 flows outward. This cooling air 85 cools the rear surface of the disk 42 and prevents hot gas 30 from flowing through the surface of the disk. '-10- The size of this paper is free to use China National Standards (CNS) A4 specifications (210X297 public director 1 (please read the precautions on the back before filling out this page) Order 32S319 A7 B7 Ministry of Economic Affairs Central Bureau of Precision Industry Beigong Consumer Cooperative Printing 5. Description of the invention 8) The second flow path 86 flows through the annular zigzag seal flow path, and then flows radially outward into the hot gas 30 flowing through the turbine section 3. Cooling the air 86 in this way cools the front surface of the disk 43 and prevents hot gas 30 from flowing through the surface of the disk. Because the pressure of the hot gas 30 flowing through the third row of rotating blades 23 is lower than the pressure of the hot gas 30 flowing through the second row of rotating blades 21, if there is no seal 72, all the cooling air will flow down to the disk 43, The seal 72 prevents it from occurring, thereby ensuring the cooling of the upstream disc 42. The disc groove cooling air supply pipe 45 allows the cooling air 84 to flow through the blades 22 to absorb the minimum heat. Therefore, according to an important feature of the present invention, the pipe 45 allows the cooling air 84 from the manifold 26 to the interstage groove 70, 43 does not substantially increase the cooling air temperature 'thereby ensuring its ability to cool the discs 42, 43. As mentioned above, 'this is particularly important in the drip wheel' because the temperature of the cooling air 19 supplied to the manifold 26 is already quite high. A plurality of fins 60-64 according to the present invention are sometimes referred to as spoilers, protruding from the walls 46, 47 in the flow paths 51_55, as shown in FIGS. 3, 5, 6, and 7. In FIG. 2, the fins 60-64 are preferably distributed substantially along the height of the entire flow path 51-55. In addition, as shown in FIG. 3, the fins 60-64 are preferably substantially along the flow path 5 1-55. The entire axial length extends. Fig. 6 shows the fins 61 of the second flow path 52, but it is a typical arrangement of the fins in each flow path. In Fig. 6, the fins 61 protrude laterally from the leaves 46, 47 opposite to the surface 37. The second flow path preferably has a height of about 10% of the width of the flow path. The fins 61 are separated so that the fins protruding from the wall 46 are arranged between the fins protruding from the wall 47. The fins 6J3-64 increase the disturbance of the cooling air 80, 83 flowing through the flow path, to Increase its cooling efficiency 〇-11- This paper scale is applicable to the Chinese National Standard (CNS) A4 specification (2 丨 0X297mm) (please read the notes on the back before filling this page) t Order squat: A7 Β7 5 Description of the invention (9) According to an important feature of the present invention, the fins 60-64 and the cooling air flow through the flow paths 51-55 form an angle, the cooling air is basically radial, so as shown in Figure 7, heat The angle between the fin and the radial direction is an acute angle a. In a preferred embodiment, the acute angle A formed with the outward radial direction is about 45-60 °, mostly 45 °. This situation occurs when the fins extend upstream The flow direction of the hot compressed gas 30 is at an angle radially outwards such as the first, third, and fourth flow paths; or the fins extend upward at an angle radially outwards, such as the second and fourth flow paths 0 The cooling air 80 flows radially inward from the outer cover ring 38 to the inner cover ring 36 in the first flow path 51. According to the invention Another important feature is that the fins 60 of the first flow path 51 are angled so that they extend radially inward v, that is, toward the inner cover ring%. This occurs when the fins extend toward the leading edge in the upstream direction, such as Circles 3 and 7. Therefore, when the cooling air 80 flows radially inward, it is directed to the front edge, as indicated by the arrow 81 in Fig. 7. Therefore, the cooling fins 60 not only increase the disturbance of the cooling air 80, but also Guide it against the leading edge 40 to increase the cooling efficiency of the leading edge. This is important because the hot gas 30 flowing through the turbine section 3 directly impacts the leading edge 40, and the leading edge is the most likely to cause overheating in the blade surface 37 Part of the production. Du printed by the National Bureau of Standards of the Ministry of Economic Affairs and the Ministry of Economic Affairs (please read the precautions on the back before filling out this page). Cool the air 80, 83 in the fifth flow path 55 radially inward from the inner cover ring 36 Flow to the outer cover ring 3. Therefore, an arrangement similar to that in the first flow path 51 is used so that the fins 64 of the first, fifth, and fourth paths 55 are angled so that they are directed radially outward, that is, toward the outer cover The extension of the ring 38 occurs when the fins extend toward the trailing edge 41 in the downstream direction, as shown in FIG. 3. Therefore, when The cooling air 8〇, 83 is directed radially outwards, that is, it is guided against the trailing edge 40 to increase the cooling efficiency of the trailing edge. This is also important because its section is thin, and the trailing edge 41 is in the leaf surface 37 Another easy • 12--t ί ι * /

* $ V 經濟部中央梂準局貝工消費合作社印裝 Α7 Β7 五、發明説明（ 產生過熱的部分。 如上所述，自第一流路51流到第二流路52時，内覆環36 使冷卻空氣轉了180。。這種方向的突然改變使得冷卻空氣 過實曲時會有流體分離的傾向。我們並不期望這種流禮 分離現象，因爲.它會降低冷卻空氣流過流路時的速度。因 此根據本發明（另-重要特色，在第二流路52中使散熱片 61成一角度以延緩冷卻空氣產生流體分離的傾向，以使其 徑向向外，即朝向外覆環38延伸，此發生於散熱片在上游 方向朝分隔第一及第二流路之壁65延伸時，因此當冷卻空 氣80完成轉向時，即引導其流向分隔65，如圖7的箭號82所 示。這種引導冷卻空氣80朝著分隔壁65，而非離開它，以 及冷卻空氣轉向時朝著冷卻空氣旋轉方向，可抑制流體分 離之傾向。 根據本發明這種分別在第三、第四及第五流路53·55定向 散熱片之設計也可實行，因此如囷7所示，第三流路53的散 熱片62是有角度的’以使其徑向向内’即朝向内覆環36延 伸’此發生於散熱片在上游方向朝分隔第二及第三流路之 壁66延伸時。同理如圖3所示，第四流路54的散熱片63是有 角度的，以使其徑向向外，即朝向外覆環38廷伸，此發生 於教熱片在上游方向朝分隔第三及第四流路之壁67延伸 時’而第五流路55的散熱片64是有角度的，以使其徑向向 内’即朝向内覆環36延伸，此發生於散熱片在上游方每朝 分隔第四及第五流路之壁68延伸時。 ， 因此散熱片60-64的方向與各後續流路相反，此發生於散 -13- —7 丨~：-----f----—-I.IT------衊丨 (請先《讀背面之注意Ϋ項再填寫本頁) 本紙法尺度適用中國國家橾準（（^5)八4*1格（210‘；<297公釐） A7 B7 五 、發明説明（ 熱片沿著流路長度延伸時其在那個角度之延伸。 因此’散熱片61-64不僅增加冷卻空氣8〇的擾動，而且藉 著抑制流趙分離以増加其流過流路5 U5之速度。 雖然本發明已藉著參考氣渦輪第三排渦輪葉片而加以説 明’本發明仍淹用於其他排葉片，以及他種重視葉面冷卻 效率之渦輪》因此只要不違反本發明之精神或基本屬性， 本發明亦可以它種特定形式實現，因此應該參考附屬的申 碕專利範圍，而非上述之規格，以作爲本發明之範圍。 (請先閎讀背面之注意事項再填寫本頁} 訂 經濟部中央棣準局工消費合作社印製 •14-* $ V Printed by the Central Bureau of Economic Affairs of the Ministry of Economic Affairs Beigong Consumer Cooperative Α7 Β7 V. Description of the invention (The part that generates overheating. As mentioned above, when flowing from the first flow path 51 to the second flow path 52, the inner cover ring 36 makes The cooling air turns 180. This sudden change in direction makes the cooling air tend to separate when it is too curved. We do not expect this flow separation phenomenon because it will reduce the cooling air when flowing through the flow path. Therefore, according to the present invention (another important feature, the fins 61 are angled in the second flow path 52 to delay the cooling air's tendency to separate fluids, so that it is radially outward, that is, toward the outer cover ring 38 Extension, which occurs when the fins extend in the upstream direction toward the wall 65 separating the first and second flow paths, so when the cooling air 80 completes turning, it is directed to flow to the partition 65, as shown by arrow 82 in FIG. 7 This guide cooling air 80 is directed toward the partition wall 65 instead of leaving it, and the cooling air is turned toward the direction of rotation of the cooling air, which can suppress the tendency of fluid separation. According to the present invention, the third, fourth and fourth First The design of the directional fins of the flow path 53 · 55 can also be implemented, so as shown in FIG. 7, the fins 62 of the third flow path 53 are angled 'to make it radially inward', that is, extend toward the inner cover ring 36 'This occurs when the fins extend in the upstream direction toward the wall 66 separating the second and third flow paths. Similarly, as shown in FIG. 3, the fins 63 of the fourth flow path 54 are angled so that their diameter Outwardly, that is, toward the outer cover ring 38, this occurs when the thermal plate extends in the upstream direction toward the wall 67 separating the third and fourth flow paths, and the fins 64 of the fifth flow path 55 are angled , So that it extends radially inward, that is, toward the inner cover ring 36, which occurs when the fins extend upstream toward the wall 68 separating the fourth and fifth flow paths. Therefore, the fins 60-64 The direction is opposite to each subsequent flow path. This happens in San-13--7 丨 ~: ----- f ------ I.IT ------ disgusting 丨 (please read Please pay attention to item Ϋ and fill in this page again) This paper method is applicable to the Chinese National Standard ((^ 5) 8 4 * 1 grid (210 '; < 297 mm) A7 B7 V. Description of invention (The length of the heat sheet along the flow path When it is extended The extension of the heat sink. Therefore, the heat sink 61-64 not only increases the disturbance of the cooling air 80, but also increases the speed of the flow through the flow path 5 U5 by suppressing the separation of the flow Zhao. Although the present invention has referenced the third Row of turbine blades to illustrate 'The present invention is still submerged in other rows of blades, and other turbines that attach importance to blade surface cooling efficiency. Therefore, as long as it does not violate the spirit or basic attributes of the present invention, the present invention can be implemented in other specific forms Therefore, the scope of the present invention should be referred to the scope of the attached patent application, rather than the above specifications. (Please read the precautions on the back before filling out this page.) Printed by the Ministry of Economic Affairs, Central Bureau of Industry and Consumer Cooperatives • 14-

Claims (1)

323319 A8 B8 C8 D8 六、申請專利範圍 2. 經濟部中央揉準局貝工消费合作社印製 一種渦輪機，包括： a) —壓縮機，以產生壓縮流體； b) —燃燒器，以加熱該壓縮流體之第—部分，藉 生一熱壓縮氣；及 產 c) 一滿輪，*以膨脹該熱壓縮氣，該渦輪之中具有—固 定葉片，以引導該熱壓縮氣之流向，該葉片乏中具有至 少弟及第二冷卻流趙流路，該第一流路具有裝置，〆 容納該壓缩流體之第二部分，該第一及第二流路循序= 流體流通，藉此該壓縮流體之該第二部分循序流過該第 一流路，接著流過第二流路，該第二流路具有裝置，以 容納該壓縮機送出之該壓縮流體之第三部分，此部分旁 通該第一流路，藉此混合該恩縮流體之該第二及第三部 分，並流過該第二流路。 根據申請專利範圍第i項之落輪機，其中該渦輪葉片又 包括一第三冷卻流體流路，該第三流路係循序與該第一 及第二流路作流體流通，藉此該壓縮流體之第二部分擴 序自該第三流路流到該第一流路，及流到該第二流路， 該壓縮流體之第三部分旁通該第一及第三流珞， 根據申請專利範圍第2項之渦輪機，其中該渦輪葉片又 广包^·: ’ a)前緣及後緣部分；％ b)—第四冷卻流體流路，該第四流路係循序與該矛二 流路作流體流通，藉此該壓縮流體之第二及第三'部分自 該第二流路流到該第四流路；及 15 本紙張尺度逋用中國國家揉準（CNS ) A4洗格（210X297公釐） (請先H讀背面之注意事項再填寫本頁) 訂 — 經濟部中央揉準局貝工消費合作社印製 A8 B8 C8 D8 六、申請專利範圍 C )複數條第五冷卻流體流路，其排列於該後緣部分， 並與該第四流路作流體流通，藉此該壓縮流體之該第二 及第二部分自該第四流路流到該第五流路。 4.根據申請專利範圍第2項之渦輪機，其中該葉片具有一 外覆環，此外覆環在該葉片上形成，用以容纳該壓縮流 體之第-二部分之該裝置，包括一開口，此開tr在該外覆 環中形成》 5 '根據中請專利範圍第1項之渦輪機，其中該葉片又包 括： a) 内覆環及外覆環，·及 b) —導管，延伸通過該内覆環及外覆環，並延伸通過 該冷卻流趙流路之一 9 6·根據申請專利範圍第5項之渦輪機’其中該導管具有一 入口’而其中該渦輪又包括—歧管，此歧管與該裝置作 流體流通，該裝置用以容納該壓縮流體之該第三部分， 而且與該導管入口作流體流通。 7·根據申請專利範圍第5項之渦輪機，其中該導管具有— 人口，以容納該壓縮流體之該第四部分。 8根據申請專利範圍第7項之渦輪機，其中該渦輪又包 (括：一轉子，一槽，此槽係在該葉片内覆環及該轉子間 形成’而其中該導管具有一—出口，此出口與該槽作流體 流通’藉此該導管引導該壓縮流體之該第四部分流專該 内復環及外覆環，與流過該流路之該—而到達該褚。 9.根據申請專利範圍第1項之渦輪機，其中該渦輪機葉片 -16· 尽紙狀財轉丰（CNS ) A4«^ ( 21GX297公羞） (请先閱讀背面之注意事項再填寫本X) 訂 A8 B8 C8 D8 申請專利範圍 又包括： a) —第三冷卻流體流路，該第—流路係循 况路作流趙流通，藉此該㈣流@之第三部分自該第: 流路，循序流到該第-流路再流到第二流路； 一 b) 第-及第二壁，圍燒該第—及第三流路； Ο複數個第-散熱片’自該壁之__延伸進人該第三流 路》及 d)複數個第二散熱片，自該壁之一延伸進入該 路。 10.根據申請專利範圍第9项之竭輪機，其中該第一及第三 流路徑向延伸通過該葉片，而其中該第一及第二散熱片 係皂徑向成一角度。 U.根據申請專利範圍第10項之渦輪機，其中該第-組散 …、片係成角度，當其在上游方向相對該熱麼縮氣流過 该渦輪而延伸時，藉此可徑向向内延伸，而其中該第二 组散熱片係成一角度，當其在下游方向相對該熱壓縮氣 流過該渦輪而延伸時，藉此可徑向向内延伸。 12.根據申請專利範固第u項之渦輪機.，其中該渦輪機葉 片具有前緣及後緣部分，該第三流路係形成於該前緣部 #分。 13··—種渦輪固定葉片，包括：〜 a) 前緣及後緣與第一及第二端； b) 第一及第二冷卻流趙流路，該第二流路係連·接該第 I 一流路藉此循序作流體流通； -17- 本紙張尺度逋用中B國家梯準（CMS ) A4说格（210X297公釐） (請先閱讀背面之注意事項再填窝本X ) 訂 經濟部中央標準局異工消背合作社印製 A8 B8 C8 D8 經濟部中央揉準局負工消费合作社印«. 申請專利範圍 c) 複數個第一散熱片’突出該第一流路 散熱片成-角度’當其㈣該前緣延伸時 葉片之該第一端延伸；及 藉此朝著該 d) 複數個第二散熱片，突出該第二流路 散熱片成4度’當其朝著該前緣延 葉片之該第二端延伸。 無此朝者孩 根據申請專利範圍第13項之渦輪葉片，又勺括 二【:冷r禮流路，其連接該第二二藉此循序 b)複數個第三散熱片，突出該第三流路内，該第三组 散熱片成一角度，當其朝著該前緣延伸時，藉^朝^該 葉片之該第一端延伸。 ^ 15.根據申請專利範圍第13項之渦輪葉片，其中該第—流 路具有裝置，以引導冷卻流體自該葉片之該第二端朝^ 該第一端。 根據申請專利範園第13項之渦輪葉片，其中該葉片之該 第一端係徑向向内離開該第二端排列，而其中該第一流 路係相鄰該前緣排列。 17· —種渦輪固定葉片，包括： '‘a)前緣及後緣與第一及第二端.； b) 裝置，用以容纳一冷卻流趙之流動； c) 一第一流路’與該緣之一相鄰排列，該第一流普具 有襞置’以引導該冷卻流禮自該第二端朝著該第端之 方向流動；及 -18 ΜΛ張尺度埴用中蹰國家標準（CNS ) A4規格（210X297公釐） (請先閲讀背面之注^h項再填寫本頁) -^, 9 1 3 3 2 3 8 8 8 8 ABCD 經濟部中央梂準局貝工消費合作社印製 六、申請專利範圍 d)複數個第一散熱片，延伸進入該第一流路，該第— 组散熱片成-角度，當其在該第—流路内朝著與該第一 流路相鄰之該數緣之該—延伸時，藉此朝著該葉片之該 第一端延伸。 18·根據申請專利範圍第17項之渦輪葉片，又包括： a) —第二流路，與該第一流路循序作流體流通，藉此 該冷卻流體自該第一流路流到該第二流路，該第二流路 具有裝置，以引導該冷卻流禮自該葉片之該第一端朝著 該第二端之方向流動； b) —壁’排列在該第一及該第二流路之間； Ο轉向裝置，當該冷卻流體之該流動自該第一流路流 到該第二流路時，用以使其轉向；及 d)裝置’當該轉向裝置轉向該冷卻流體時，用以延缓 該冷卻流體之流體分離。 I9·根據申請專利範圍第18項之渦輪葉片，其中用以延緩 流體分離之該裝置，包括複數個第二散熱片，延伸進入 該第二流路，該第二组散熱片成—角度，當其在該第二 流路内朝著該壁延伸時，藉此朝著該葉片之該第二端延 伸。 20·,根璩申請專利範圍第19項之渦輪葉片，其中該轉向裝 置包括一覆環，此覆環在該、葉片之第一端上形成，及具 有裝置，以轉向該冷卻流體之該流動約1 8 〇。。 〜 -19- 本紙張尺度適用中國國家標率（CNS ) A4規格（210X297:釐） (請先Η讀背面之注f項再填窝本頁) 订323319 A8 B8 C8 D8 VI. Scope of patent application 2. The Ministry of Economic Affairs, Central Bureau of Economic Development, Beigong Consumer Cooperative printed a turbine, including: a)-compressor to produce compressed fluid; b)-burner to heat the compression The first part of the fluid, which generates a hot compressed gas; and c) a full wheel, * to expand the hot compressed gas, the turbine has-fixed blades to guide the flow of the hot compressed gas, the blade is exhausted There is at least a brother and a second cooling flow channel, the first channel has a device, 〆 accommodates the second part of the compressed fluid, the first and second channels are in order = fluid circulation, whereby the second of the compressed fluid Partially flows through the first flow path, then flows through the second flow path, the second flow path has a device to accommodate the third part of the compressed fluid sent by the compressor, this part bypasses the first flow path, by The second and third parts of the constricted fluid are mixed and flow through the second flow path. According to item i of the patent application scope, the turbine blade further includes a third cooling fluid flow path, the third flow path is in fluid communication with the first and second flow paths in sequence, whereby the compressed fluid The second part of the second part expands from the third flow path to the first flow path and to the second flow path, and the third part of the compressed fluid bypasses the first and third flow paths, according to the scope of the patent application Item 2 of the turbine, wherein the turbine blade is also widely covered ^ ·: 'a) leading edge and trailing edge parts;% b)-the fourth cooling fluid flow path, the fourth flow path is sequentially operated with the spear two flow path Fluid circulation, whereby the second and third portions of the compressed fluid flow from the second flow path to the fourth flow path; and 15 sheets of paper using the Chinese National Standard (CNS) A4 washing grid (210X297 Cli) (please read the precautions on the back before filling in this page) Order — A8 B8 C8 D8 printed by the Beigong Consumer Cooperative of the Central Bureau of Economic Development of the Ministry of Economy VI. Patent application scope C) plural fifth cooling fluid flow paths, It is arranged on the trailing edge portion and is in fluid communication with the fourth flow path Whereby the second and the second portion of the compressed fluid flows from the fourth channel of the fifth passage. 4. The turbomachinery according to item 2 of the patent application, wherein the blade has an outer covering ring, and the covering ring is formed on the blade to accommodate the device of the second part of the compressed fluid, including an opening, which The opening tr is formed in the outer cladding ring. 5 'The turbine according to item 1 of the patent application, wherein the blades also include: a) an inner cladding ring and an outer cladding ring, and b) — a duct extending through the inner ring Covering ring and outer covering ring, and extending through one of the cooling flow Zhao flow path 9 6. According to the patent application item 5 of the turbine 'where the duct has an inlet' and where the turbine further includes a manifold, this manifold is The device is in fluid communication. The device is used to contain the third portion of the compressed fluid and in fluid communication with the conduit inlet. 7. The turbine according to item 5 of the patent application scope, wherein the conduit has a population to accommodate the fourth part of the compressed fluid. 8. The turbine according to item 7 of the patent application scope, wherein the turbine further includes (including: a rotor, a slot, the slot is formed between the covering ring and the rotor in the blade and the duct has an outlet, which The outlet and the groove are in fluid communication 'whereby the conduit guides the fourth part of the compressed fluid to the inner complex ring and the outer cover ring, and the one flowing through the flow path to reach the Chu. 9. According to the application The turbine in the first item of the patent scope, in which the turbine blades-16 · make paper-like wealth (CNS) A4 «^ (21GX297 public shame) (please read the precautions on the back before filling in this X) Order A8 B8 C8 D8 The scope of the patent application includes: a)-the third cooling fluid flow path, the first-flow path is a flow path that flows through the flow path, so that the third part of the flow @ from the first: flow path, flow to The first-flow path then flows to the second flow path; 1b) The second- and second walls enclose the first- and third flow paths; Ο A plurality of first-fins extend from the wall __ "The third flow path" and d) a plurality of second fins extend from one of the walls into the path. 10. The exhaust turbine according to item 9 of the patent application scope, wherein the first and third flow paths extend through the blade, and wherein the first and second fins are soap at an angle radially. U. The turbomachinery according to item 10 of the patent application scope, wherein the first-group diffuser is angled so that when it extends in the upstream direction with respect to the heat-shrinkable airflow through the turbine, it can be radially inward Extending, and wherein the second set of fins is at an angle, and when it extends in the downstream direction relative to the hot compressed air flow through the turbine, it can extend radially inwardly. 12. The turbomachine according to the patent application No. u, wherein the turbine blade has a leading edge and a trailing edge portion, and the third flow path is formed at the leading edge portion. 13 ·· —A turbine fixed blade, including: ~ a) The leading and trailing edges and the first and second ends; b) The first and second cooling flow channels, the second channel is connected to the first The first-class road is used for fluid circulation in sequence; -17- This paper uses the National B Standard (CMS) A4 standard (210X297mm) (please read the precautions on the back before filling the nest X). Order the Ministry of Economy A8 B8 C8 D8 printed by the Central Standards Bureau Cooperative Cooperative Cooperative of the Ministry of Economic Affairs of the Ministry of Economic Affairs of the Ministry of Economic Affairs «. The scope of patent application c) a plurality of first heat sinks 'protruding the first flow path heat sink into-angle' When the (i) the leading edge extends, the first end of the blade extends; and thereby a plurality of second fins protruding toward the d) protruding the second flow path fins by 4 degrees as it moves toward the leading edge The second end of the extended blade extends. Without this, according to the turbine blade of item 13 of the patent application scope, it also includes two [: cold flow channels, which are connected to the second two to thereby sequentially b) a plurality of third fins, highlighting the third In the flow path, the third set of fins is at an angle, and when it extends toward the leading edge, it extends toward the first end of the blade. ^ 15. The turbine blade according to item 13 of the patent application scope, wherein the first flow path has a device to guide the cooling fluid from the second end of the blade toward the first end. According to the turbine blade of claim 13, the first end of the blade is arranged radially inwardly away from the second end, and wherein the first flow path is arranged adjacent to the leading edge. 17 ·-Turbine fixed blades, including: '' a) leading and trailing edges and first and second ends .; b) a device to accommodate a cooling flow of Zhao; c) a first flow path 'and One of the edges is arranged adjacent to each other, the first stream has a fold to guide the cooling flow from the second end to the direction of the first end; and -18 ΜΛ Zhang scale using the Chinese National Standard (CNS ) A4 specification (210X297 mm) (please read the note ^ h on the back and then fill in this page)-^, 9 1 3 3 2 3 8 8 8 8 ABCD Printed by the Central Bureau of Economic Affairs of the Ministry of Economic Affairs Beigong Consumer Cooperative 6 、 Patent application range d) A plurality of first fins extend into the first flow path, the first group of fins form an angle, when it is in the first flow path toward the adjacent to the first flow path The extension of the number edge extends toward the first end of the blade. 18. The turbine blade according to item 17 of the patent application scope further includes: a)-a second flow path, which is in fluid communication with the first flow path in sequence, whereby the cooling fluid flows from the first flow path to the second flow Path, the second flow path has means to guide the cooling flow from the first end of the blade toward the direction of the second end; b) —the walls are arranged in the first and the second flow path Between; Ο steering device, when the flow of the cooling fluid flows from the first flow path to the second flow path, to turn it; and d) device 'when the steering device turns to the cooling fluid, use To delay the fluid separation of the cooling fluid. I9. The turbine blade according to item 18 of the patent application, wherein the device for delaying fluid separation includes a plurality of second fins extending into the second flow path, the second group of fins form an angle, when When it extends toward the wall in the second flow path, it thus extends toward the second end of the blade. 20 ·, the turbine blade of the 19th patent application scope of Genza, wherein the steering device includes a covering ring formed on the first end of the blade and having a device to divert the flow of the cooling fluid About 1 8 〇. . ~ -19- This paper scale is applicable to China National Standard (CNS) A4 specification (210X297: PCT) (please read note f on the back and fill in this page)
TW084110282A 1994-10-31 1995-10-03 TW323319B (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
TWI409383B (en) * 2007-09-24 2013-09-21 Alstom Technology Ltd Seal in gas turbine

Families Citing this family (93)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0791127B1 (en) * 1994-11-10 2000-03-08 Siemens Westinghouse Power Corporation Gas turbine vane with a cooled inner shroud
US5645397A (en) * 1995-10-10 1997-07-08 United Technologies Corporation Turbine vane assembly with multiple passage cooled vanes
GB2307520B (en) * 1995-11-14 1999-07-07 Rolls Royce Plc A gas turbine engine
US5630700A (en) * 1996-04-26 1997-05-20 General Electric Company Floating vane turbine nozzle
WO1998000627A1 (en) * 1996-06-28 1998-01-08 United Technologies Corporation Coolable airfoil for a gas turbine engine
US5842829A (en) * 1996-09-26 1998-12-01 General Electric Co. Cooling circuits for trailing edge cavities in airfoils
US5775091A (en) * 1996-10-21 1998-07-07 Westinghouse Electric Corporation Hydrogen fueled power plant
JP3416447B2 (en) * 1997-03-11 2003-06-16 三菱重工業株式会社 Gas turbine blade cooling air supply system
JP3426902B2 (en) * 1997-03-11 2003-07-14 三菱重工業株式会社 Gas turbine cooling vane
JP3316415B2 (en) * 1997-05-01 2002-08-19 三菱重工業株式会社 Gas turbine cooling vane
DE69825959T2 (en) * 1997-06-19 2005-09-08 Mitsubishi Heavy Industries, Ltd. DEVICE FOR SEALING GUIDING TUBE GUIDES
EP0892150B1 (en) * 1997-07-14 2003-02-05 ALSTOM (Switzerland) Ltd System for cooling the trailing edge of a hollow gasturbine blade
US6430931B1 (en) * 1997-10-22 2002-08-13 General Electric Company Gas turbine in-line intercooler
JPH11173105A (en) * 1997-12-08 1999-06-29 Mitsubishi Heavy Ind Ltd Moving blade of gas turbine
US6139269A (en) * 1997-12-17 2000-10-31 United Technologies Corporation Turbine blade with multi-pass cooling and cooling air addition
US6146091A (en) * 1998-03-03 2000-11-14 Mitsubishi Heavy Industries, Ltd. Gas turbine cooling structure
ITMI991208A1 (en) * 1999-05-31 2000-12-01 Nuovo Pignone Spa DEVICE FOR THE POSITIONING OF NOZZLES OF A STATIC STAGE AND FOR THE COOLING OF ROTOR DISCS IN GAS TURBINES
EP1200744B1 (en) * 1999-07-29 2005-04-06 Siemens Aktiengesellschaft Device and method for controlling a cooling air flow of a gas turbine and gas turbine with a cooling air flow
US6241467B1 (en) 1999-08-02 2001-06-05 United Technologies Corporation Stator vane for a rotary machine
US6254333B1 (en) 1999-08-02 2001-07-03 United Technologies Corporation Method for forming a cooling passage and for cooling a turbine section of a rotary machine
US6398488B1 (en) * 2000-09-13 2002-06-04 General Electric Company Interstage seal cooling
US6558114B1 (en) * 2000-09-29 2003-05-06 Siemens Westinghouse Power Corporation Gas turbine with baffle reducing hot gas ingress into interstage disc cavity
DE10064264B4 (en) * 2000-12-22 2017-03-23 General Electric Technology Gmbh Arrangement for cooling a component
EP1245806B1 (en) * 2001-03-30 2005-08-03 Siemens Aktiengesellschaft Cooled gas turbine balde
US6508620B2 (en) * 2001-05-17 2003-01-21 Pratt & Whitney Canada Corp. Inner platform impingement cooling by supply air from outside
GB2381298A (en) * 2001-10-26 2003-04-30 Rolls Royce Plc A turbine blade having a greater thickness to chord ratio
US6776873B1 (en) * 2002-02-14 2004-08-17 Jennifer Y Sun Yttrium oxide based surface coating for semiconductor IC processing vacuum chambers
US6769865B2 (en) 2002-03-22 2004-08-03 General Electric Company Band cooled turbine nozzle
US6884023B2 (en) * 2002-09-27 2005-04-26 United Technologies Corporation Integral swirl knife edge injection assembly
US7118326B2 (en) * 2004-06-17 2006-10-10 Siemens Power Generation, Inc. Cooled gas turbine vane
US7137780B2 (en) * 2004-06-17 2006-11-21 Siemens Power Generation, Inc. Internal cooling system for a turbine blade
US7007488B2 (en) * 2004-07-06 2006-03-07 General Electric Company Modulated flow turbine nozzle
US7435053B2 (en) * 2005-03-29 2008-10-14 Siemens Power Generation, Inc. Turbine blade cooling system having multiple serpentine trailing edge cooling channels
EP1728973A1 (en) * 2005-06-01 2006-12-06 Siemens Aktiengesellschaft Method to block a clearance in a Turbomachine and Turbomachine to carry out the method
GB0523469D0 (en) * 2005-11-18 2005-12-28 Rolls Royce Plc Blades for gas turbine engines
US7303376B2 (en) * 2005-12-02 2007-12-04 Siemens Power Generation, Inc. Turbine airfoil with outer wall cooling system and inner mid-chord hot gas receiving cavity
US20070151257A1 (en) * 2006-01-05 2007-07-05 Maier Mark S Method and apparatus for enabling engine turn down
US7669425B2 (en) * 2006-10-25 2010-03-02 Siemens Energy, Inc. Closed loop turbine cooling fluid reuse system for a turbine engine
US10622194B2 (en) 2007-04-27 2020-04-14 Applied Materials, Inc. Bulk sintered solid solution ceramic which exhibits fracture toughness and halogen plasma resistance
US10242888B2 (en) 2007-04-27 2019-03-26 Applied Materials, Inc. Semiconductor processing apparatus with a ceramic-comprising surface which exhibits fracture toughness and halogen plasma resistance
US7775769B1 (en) 2007-05-24 2010-08-17 Florida Turbine Technologies, Inc. Turbine airfoil fillet region cooling
DE102007027427A1 (en) * 2007-06-14 2008-12-18 Rolls-Royce Deutschland Ltd & Co Kg Bucket cover tape with overhang
WO2008155248A1 (en) * 2007-06-20 2008-12-24 Alstom Technology Ltd Cooling of the guide vane of a gas turbine
US7785072B1 (en) 2007-09-07 2010-08-31 Florida Turbine Technologies, Inc. Large chord turbine vane with serpentine flow cooling circuit
US7946801B2 (en) * 2007-12-27 2011-05-24 General Electric Company Multi-source gas turbine cooling
WO2009118235A2 (en) * 2008-03-28 2009-10-01 Alstom Technology Ltd Guide vane for a gas turbine
ES2542064T3 (en) * 2008-03-28 2015-07-30 Alstom Technology Ltd Guide blade for a gas turbine and gas turbine with a guide blade of this class
WO2009118234A1 (en) * 2008-03-28 2009-10-01 Alstom Technology Ltd Blade for a rotating thermal engine
US8408866B2 (en) * 2008-11-17 2013-04-02 Rolls-Royce Corporation Apparatus and method for cooling a turbine airfoil arrangement in a gas turbine engine
US8096772B2 (en) * 2009-03-20 2012-01-17 Siemens Energy, Inc. Turbine vane for a gas turbine engine having serpentine cooling channels within the inner endwall
US8328518B2 (en) * 2009-08-13 2012-12-11 Siemens Energy, Inc. Turbine vane for a gas turbine engine having serpentine cooling channels
US9528382B2 (en) * 2009-11-10 2016-12-27 General Electric Company Airfoil heat shield
US8628294B1 (en) * 2011-05-19 2014-01-14 Florida Turbine Technologies, Inc. Turbine stator vane with purge air channel
US8702375B1 (en) * 2011-05-19 2014-04-22 Florida Turbine Technologies, Inc. Turbine stator vane
US9062557B2 (en) * 2011-09-07 2015-06-23 Siemens Aktiengesellschaft Flow discourager integrated turbine inter-stage U-ring
EP2805018A1 (en) * 2011-12-29 2014-11-26 General Electric Company Airfoil cooling circuit
EP2713009B1 (en) * 2012-09-26 2015-03-11 Alstom Technology Ltd Cooling method and system for cooling blades of at least one blade row in a rotary flow machine
US9476308B2 (en) * 2012-12-27 2016-10-25 United Technologies Corporation Gas turbine engine serpentine cooling passage with chevrons
DE102013011350A1 (en) 2013-07-08 2015-01-22 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine with high pressure turbine cooling system
US10240470B2 (en) * 2013-08-30 2019-03-26 United Technologies Corporation Baffle for gas turbine engine vane
US9518478B2 (en) 2013-10-28 2016-12-13 General Electric Company Microchannel exhaust for cooling and/or purging gas turbine segment gaps
WO2015169555A1 (en) * 2014-05-08 2015-11-12 Siemens Aktiengesellschaft Turbine assembly and corresponding method of operation
EP2944762B1 (en) * 2014-05-12 2016-12-21 General Electric Technology GmbH Airfoil with improved cooling
US11033845B2 (en) * 2014-05-29 2021-06-15 General Electric Company Turbine engine and particle separators therefore
CA2949547A1 (en) 2014-05-29 2016-02-18 General Electric Company Turbine engine and particle separators therefore
EP3081751B1 (en) 2015-04-14 2020-10-21 Ansaldo Energia Switzerland AG Cooled airfoil and method for manufacturing said airfoil
US10012092B2 (en) * 2015-08-12 2018-07-03 United Technologies Corporation Low turn loss baffle flow diverter
EP3156595A1 (en) * 2015-10-12 2017-04-19 Siemens Aktiengesellschaft Channelling tube and method for manufacturing a channelling tube
US10125632B2 (en) 2015-10-20 2018-11-13 General Electric Company Wheel space purge flow mixing chamber
US10132195B2 (en) 2015-10-20 2018-11-20 General Electric Company Wheel space purge flow mixing chamber
US10508554B2 (en) 2015-10-27 2019-12-17 General Electric Company Turbine bucket having outlet path in shroud
US10156145B2 (en) * 2015-10-27 2018-12-18 General Electric Company Turbine bucket having cooling passageway
US9885243B2 (en) 2015-10-27 2018-02-06 General Electric Company Turbine bucket having outlet path in shroud
US20170198602A1 (en) * 2016-01-11 2017-07-13 General Electric Company Gas turbine engine with a cooled nozzle segment
CA2954785A1 (en) 2016-01-25 2017-07-25 Rolls-Royce Corporation Forward flowing serpentine vane
US10519873B2 (en) 2016-04-06 2019-12-31 General Electric Company Air bypass system for rotor shaft cooling
US10352182B2 (en) 2016-05-20 2019-07-16 United Technologies Corporation Internal cooling of stator vanes
CN105971674B (en) * 2016-07-29 2018-04-03 上海电气燃气轮机有限公司 Gas turbine wheel rim sealing structure and method
US10876407B2 (en) * 2017-02-16 2020-12-29 General Electric Company Thermal structure for outer diameter mounted turbine blades
US10837291B2 (en) 2017-11-17 2020-11-17 General Electric Company Turbine engine with component having a cooled tip
US10502093B2 (en) * 2017-12-13 2019-12-10 Pratt & Whitney Canada Corp. Turbine shroud cooling
US10570773B2 (en) 2017-12-13 2020-02-25 Pratt & Whitney Canada Corp. Turbine shroud cooling
US10533454B2 (en) 2017-12-13 2020-01-14 Pratt & Whitney Canada Corp. Turbine shroud cooling
US20190234235A1 (en) * 2018-01-31 2019-08-01 United Technologies Corporation Vane flow diverter
US10669887B2 (en) * 2018-02-15 2020-06-02 Raytheon Technologies Corporation Vane airfoil cooling air communication
JP7085402B2 (en) * 2018-04-27 2022-06-16 三菱重工業株式会社 gas turbine
CN108868896A (en) * 2018-06-29 2018-11-23 北京驰宇空天技术发展有限公司 A kind of engine turbine moving blades and turbogenerator
JP7302984B2 (en) * 2019-02-22 2023-07-04 三菱重工業株式会社 Stator vanes and rotating machinery
CN111852574A (en) * 2020-07-27 2020-10-30 北京全四维动力科技有限公司 Turbine blade and gas turbine comprising same
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
US12116906B2 (en) 2021-01-06 2024-10-15 Siemens Energy Global GmbH & Co. KG Turbine vane in gas turbine engine
US11761632B2 (en) * 2021-08-05 2023-09-19 General Electric Company Combustor swirler with vanes incorporating open area
JP2023165485A (en) * 2022-05-06 2023-11-16 三菱重工業株式会社 Turbine blade and gas turbine

Family Cites Families (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR999820A (en) * 1946-01-11 1952-02-05 Improvements to gas turbines
US3171631A (en) * 1962-12-05 1965-03-02 Gen Motors Corp Turbine blade
US3220697A (en) * 1963-08-30 1965-11-30 Gen Electric Hollow turbine or compressor vane
US3628885A (en) * 1969-10-01 1971-12-21 Gen Electric Fluid-cooled airfoil
US3834831A (en) * 1973-01-23 1974-09-10 Westinghouse Electric Corp Blade shank cooling arrangement
US3945758A (en) * 1974-02-28 1976-03-23 Westinghouse Electric Corporation Cooling system for a gas turbine
US4073599A (en) * 1976-08-26 1978-02-14 Westinghouse Electric Corporation Hollow turbine blade tip closure
US4292008A (en) * 1977-09-09 1981-09-29 International Harvester Company Gas turbine cooling systems
FR2468727A1 (en) * 1979-10-26 1981-05-08 Snecma IMPROVEMENT TO COOLED TURBINE AUBES
US4416585A (en) * 1980-01-17 1983-11-22 Pratt & Whitney Aircraft Of Canada Limited Blade cooling for gas turbine engine
FR2476207A1 (en) * 1980-02-19 1981-08-21 Snecma IMPROVEMENT TO AUBES OF COOLED TURBINES
GB2163218B (en) * 1981-07-07 1986-07-16 Rolls Royce Cooled vane or blade for a gas turbine engine
US4515526A (en) * 1981-12-28 1985-05-07 United Technologies Corporation Coolable airfoil for a rotary machine
US4474532A (en) * 1981-12-28 1984-10-02 United Technologies Corporation Coolable airfoil for a rotary machine
US4775296A (en) * 1981-12-28 1988-10-04 United Technologies Corporation Coolable airfoil for a rotary machine
US4514144A (en) * 1983-06-20 1985-04-30 General Electric Company Angled turbulence promoter
GB2165315B (en) * 1984-10-04 1987-12-31 Rolls Royce Improvements in or relating to hollow fluid cooled turbine blades
JPS62271902A (en) * 1986-01-20 1987-11-26 Hitachi Ltd Cooled blade for gas turbine
JPS62228603A (en) * 1986-03-31 1987-10-07 Toshiba Corp Gas turbine blade
GB2228540B (en) * 1988-12-07 1993-03-31 Rolls Royce Plc Cooling of turbine blades
US4962640A (en) * 1989-02-06 1990-10-16 Westinghouse Electric Corp. Apparatus and method for cooling a gas turbine vane
US4930980A (en) * 1989-02-15 1990-06-05 Westinghouse Electric Corp. Cooled turbine vane
US5052889A (en) * 1990-05-17 1991-10-01 Pratt & Whintey Canada Offset ribs for heat transfer surface
US5117626A (en) * 1990-09-04 1992-06-02 Westinghouse Electric Corp. Apparatus for cooling rotating blades in a gas turbine
JP3006174B2 (en) * 1991-07-04 2000-02-07 株式会社日立製作所 Member having a cooling passage inside
US5203873A (en) * 1991-08-29 1993-04-20 General Electric Company Turbine blade impingement baffle
US5145315A (en) * 1991-09-27 1992-09-08 Westinghouse Electric Corp. Gas turbine vane cooling air insert
US5246341A (en) * 1992-07-06 1993-09-21 United Technologies Corporation Turbine blade trailing edge cooling construction
US5320483A (en) * 1992-12-30 1994-06-14 General Electric Company Steam and air cooling for stator stage of a turbine
US5387086A (en) * 1993-07-19 1995-02-07 General Electric Company Gas turbine blade with improved cooling
US5387085A (en) * 1994-01-07 1995-02-07 General Electric Company Turbine blade composite cooling circuit

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
TWI409383B (en) * 2007-09-24 2013-09-21 Alstom Technology Ltd Seal in gas turbine

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